JP5357908B2 - Axial fluid machine blades - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a blade for axial flow machine which can reduce friction loss of the blade and equipped with high surge resistance. <P>SOLUTION: In the blade 60 for an axial flow fluid machine which is employed for the axial flow fluid machine, cord length near 20%Ht and cord length near 80%Ht is formed to be shorter than that near 50%Ht when the root is 0%Ht (Ht is blade height) and the tip is 100%Ht. <P>COPYRIGHT: (C)2011,JPO&amp;INPIT

Description

  The present invention relates to a blade (for example, a stationary blade) used for an axial fluid machine (for example, an axial compressor or the like).

  As blades used in an axial fluid machine, for example, those disclosed in Patent Documents 1 and 2 are known.

Japanese Patent Laid-Open No. 10-103002 JP-A-10-184303

The wing disclosed in Patent Document 1 includes a leading edge having a substantially U-shape in plan view in which a tip portion and a root portion of the leading edge protrude toward the upstream side.
Further, the wing disclosed in Patent Document 2 includes a trailing edge having a substantially U-shape in plan view in which a tip portion and a root portion at the rear edge protrude toward the downstream side.
Now, in order to reduce the friction loss of the blade and improve the performance of the axial flow fluid machine, the surface area of the entire blade is reduced by combining the invention of Patent Document 1 and the invention of Patent Document 2. It is conceivable to improve the performance of the axial fluid machine by significantly reducing the friction loss of the blades.
However, in a wing in which the wing disclosed in Patent Document 1 and the wing disclosed in Patent Document 2 are combined, the cord length in the midspan portion is shorter than the cord length in other portions. . Therefore, at the rated point, it is possible to reduce the friction loss of the blade and improve the performance of the axial fluid machine.For example, when the operating point moves to the side of the pressure ratio larger than the rated point at high load, There is a problem that an air flow is separated at the midspan portion and a surge occurs.

  The present invention has been made in view of the above circumstances, and an object thereof is to provide a blade for an axial fluid machine that can reduce friction loss of the blade and has high surge resistance.

The present invention employs the following means in order to solve the above problems.
A blade for an axial fluid machine according to the present invention is a blade for an axial fluid machine used in an axial fluid machine, wherein a leading edge projects toward an upstream side at a tip portion and a root portion thereof, and a trailing edge is formed. The tip portion, midspan portion, and route portion are formed so as to protrude toward the downstream side, with 0% Ht (Ht is the blade height) as the root and 100% Ht as the tip. The code length in the vicinity of 20% Ht and the code length in the vicinity of 80% Ht are shorter than the code length in the vicinity of 50% Ht, and the code length in the vicinity of 50% Ht is 0% Ht. The cord length is substantially equal to the cord length at 100% Ht.
According to such an axial fluid machine blade, the front edge thereof is formed so as to have a substantially U shape in plan view, and the rear edge thereof is formed in a substantially W shape in plan view. The length is reduced and the surface area of the entire blade is reduced. Thereby, the friction loss of a wing | blade can be reduced.
In addition, the cord length of the wing, particularly in the vicinity of 20% Ht, and the cord length in the vicinity of 80% Ht can be reduced, and the surface area of these regions can be reduced. The loss can be reduced, for example, as shown by the dashed line in FIG.
Further, the code length in the vicinity of 50% Ht is longer than the code length in the vicinity of 20% Ht and the code length in the vicinity of 80% Ht ( approximately equal to the code length at 0 % Ht and the code length at 100% Ht. Therefore, even when the operating point moves to the side of the pressure ratio larger than the rated point at high load, it is possible to prevent separation of the air flow in the mid-span part, and to withstand surge resistance. A decrease can be prevented.
Furthermore, the wing is manufactured by scraping off the leading edge and the trailing edge thereof (that is, the tip part, the midspan part, and the root part are added upstream and / or downstream). Therefore, it is possible to avoid an increase in the size in the axial direction.

A blade for an axial fluid machine according to the present invention is a blade for an axial fluid machine used in an axial fluid machine, and a leading edge projects toward an upstream side in a tip part, a midspan part, and a root part. The trailing edge is formed so as to protrude toward the downstream side in the tip portion and the root portion, and 0% Ht (Ht is the blade height) is the root, and 100% Ht is the tip. The code length in the vicinity of 20% Ht and the code length in the vicinity of 80% Ht are shorter than the code length in the vicinity of 50% Ht, and the code length in the vicinity of 50% Ht is 0% Ht. The cord length is substantially equal to the cord length at 100% Ht.
According to such an axial fluid machine blade, the front edge thereof is formed so as to have a substantially W shape in plan view, and the rear edge thereof is formed in a substantially U shape in plan view. The length is reduced and the surface area of the entire blade is reduced. Thereby, the friction loss of a wing | blade can be reduced.
In addition, the cord length of the wing, particularly in the vicinity of 20% Ht, and the cord length in the vicinity of 80% Ht can be reduced, and the surface area of these regions can be reduced. The loss can be reduced, for example, as shown by the dashed line in FIG.
Further, the code length in the vicinity of 50% Ht is longer than the code length in the vicinity of 20% Ht and the code length in the vicinity of 80% Ht ( approximately equal to the code length at 0 % Ht and the code length at 100% Ht. Therefore, even when the operating point moves to the side of the pressure ratio larger than the rated point at high load, it is possible to prevent separation of the air flow in the mid-span part, and to withstand surge resistance. A decrease can be prevented.
Furthermore, the wing is manufactured by scraping off the leading edge and the trailing edge thereof (that is, the tip part, the midspan part, and the root part are added upstream and / or downstream). Therefore, it is possible to avoid an increase in the size in the axial direction.

An axial fluid machine according to the present invention includes a blade for an axial fluid machine that can reduce friction loss of the blade and has high surge resistance.
According to such an axial flow fluid machine, the performance is improved and the surge margin is improved.

  According to the present invention, it is possible to reduce the friction loss of the blade and to prevent the surge resistance from being lowered.

It is a figure which shows the gas turbine provided with the blade | wing for axial flow fluid machines by this invention, Comprising: It is a schematic perspective view which shows the state which removed the vehicle interior upper half part. It is a principal part perspective view which shows the blade | wing for axial flow fluid machines shown in FIG. 1, and the moving blade located in the back | latter stage. FIG. 3 is a plan view of the axial fluid machine blade shown in FIG. 2 as viewed along an arrow A shown in FIG. 2. It is the graph which compared the friction loss of the blade | wing for axial flow fluid machines by this invention, and the friction loss of the blade | wing for conventional axial flow fluid machines. It is a figure which shows 2nd Embodiment of the wing | blade for axial flow fluid machines by this invention, Comprising: It is a figure similar to FIG.

Hereinafter, a first embodiment of an axial fluid machine blade according to the present invention will be described with reference to the drawings.
FIG. 1 is a diagram showing a gas turbine 10 equipped with an axial fluid machine blade (hereinafter referred to as a “static blade”) 60 according to the present embodiment, and is a schematic perspective view showing a state in which the upper half of a vehicle compartment is removed. FIG.

As shown in FIG. 1, the gas turbine 10 injects and burns fuel into a compression unit (axial fluid machine) 20 that compresses combustion air, and high-pressure air sent from the compression unit 20, The main elements are a combustion section 30 that generates high-temperature combustion gas and a turbine section 40 that is located downstream of the combustion section 30 and is driven by the combustion gas that has left the combustion section 30.
The compression unit 20 includes a rotor assembly 21 and a stationary blade assembly 22.
The rotor assembly 21 includes a shaft 21a disposed on a journal bearing 51 provided in the passenger compartment 50, and a plurality of blade disks 21b provided on the shaft 21a.
The moving blade disk 21b is provided with a plurality of moving blades 21c.
The stationary blade assembly 22 is disposed adjacent to the moving blade disk 21b in the axial direction and is divided into a plurality of segments along the circumferential direction of the casing 50. In the case where the upper half and the lower half are each divided into two segments, four segments (that is, four stator vane assemblies) constitute one stage of the stator portion.
In addition, the code | symbol 26 in FIG. 1 is a diffuser.

  As shown in FIGS. 1 and 2, the stationary blade assembly 22 includes a plurality of stationary blades 60 arranged in an annular shape, and guides an air flow to the moving blade 21 c (or the diffuser 26) located at the subsequent stage. .

Next, the stationary blade 60 according to the present embodiment will be described in detail with reference to FIG. FIG. 3 is a plan view of the stationary blade 60 as viewed along the arrow A shown in FIG. 2, that is, when the stationary blade 60 is viewed from above when placed on a flat desk with its ventral side down. It is a figure which shows the outline which can be made.
In FIG. 3, the left side is the front edge side, the right side is the rear edge side, the upper side is the tip (tip) side, and the lower side is the root (root) side.

As shown in FIG. 3, the leading edge 61 of the stationary blade 60 is substantially U-shaped in a plan view in which the tip portion and the root portion protrude toward the upstream side (upstream side with respect to the flow of combustion air). It is formed to exhibit. Further, the trailing edge 62 of the stationary blade 60 has a substantially W-shape in a plan view in which the tip portion, the midspan portion, and the root portion protrude toward the downstream side (downstream side with respect to the flow of combustion air). It is formed to present. That is, the stationary blade 60 has a cord length in the vicinity of 20% Ht and a cord length in the vicinity of 80% Ht shorter than that in the vicinity of 50% Ht (in other words, the cord length in the vicinity of 20% Ht and 80 (The code length in the vicinity of% Ht is the shortest).
The code length near 50% Ht is substantially equal to the code length at 0% Ht and the code length at 100% Ht.
Further, 0% Ht is the root of the stationary blade 60, and 100% Ht is the tip of the stationary blade 60.

According to the stationary blade 60 according to the present embodiment, the front edge 61 is formed so as to have a substantially U shape in a plan view, and the rear edge 62 is formed so as to have a substantially W shape in a plan view. As a result, a reduction in the cord length and a reduction in the surface area of the entire stationary blade 60 are achieved. Thereby, the friction loss of the stationary blade 60 can be reduced.
Further, the cord length of the stationary blade 60, in particular, between the tip portion and the midspan portion and between the midspan portion and the root portion is reduced, and the surface area of these regions is reduced. Therefore, the friction loss in these regions can be reduced as shown by the broken line in FIG.
The thick solid line in FIG. 4 is for a stationary blade having a leading edge 61 shown in FIG. 3 and a trailing edge that is straight from the root to the tip (that is, has no irregularities from the root to the tip). It is.
The broken lines in FIG. 4 indicate that the code length near 25% Ht and the code length near 75% Ht are shorter than the code length near 50% Ht (in other words, the code length near 25% Ht. And so that the cord length in the vicinity of 75% Ht is the shortest).

According to the stationary blade 60 according to the present embodiment, the cord length in the vicinity of 50% Ht (mid span portion) is larger than the cord length between the tip portion and the mid span portion and between the mid span portion and the root portion. Since it is formed to be long (for example, approximately equal to the cord length at 0% Ht and the cord length at 100% Ht), the operating point is closer to the pressure ratio side than the rated point at high load. Even if it moves, separation of the air flow in the vicinity of 50% Ht (midspan portion) can be prevented, and deterioration of surge resistance can be prevented.
Further, the stationary blade 60 according to the present embodiment is manufactured by scraping off the leading edge and the trailing edge thereof (that is, the tip part, the midspan part, and the root part are added upstream and / or downstream). Therefore, it is possible to avoid an increase in the size in the axial direction.

  In the compression unit 20 including the stationary blade 60 according to the present embodiment, the performance is improved and the surge margin is improved.

A second embodiment of a stationary blade according to the present invention will be described with reference to FIG.
The stator blade 70 according to the present embodiment is described above in that the front edge 71 is formed to have a substantially W shape in plan view and the rear edge 72 is formed to have a substantially U shape in plan view. This is different from the first embodiment. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.

As shown in FIG. 5, which is a view similar to FIG. 3, the leading edge 71 of the stationary blade 70 is upstream of the tip portion, midspan portion, and root portion (upstream side of the combustion air flow). It is formed so as to exhibit a substantially W shape in plan view, protruding toward the surface. In addition, the trailing edge 72 of the stationary blade 70 is formed to have a substantially U shape in plan view with its tip portion and its root portion protruding toward the downstream side (downstream side with respect to the flow of combustion air). Has been. That is, the stationary blade 70 has a cord length in the vicinity of 20% Ht and a cord length in the vicinity of 80% Ht shorter than the cord length in the vicinity of 50% Ht (in other words, the cord length in the vicinity of 20% Ht and 80 (The code length in the vicinity of% Ht is the shortest).
The code length near 50% Ht is substantially equal to the code length at 0% Ht and the code length at 100% Ht.
Further, 0% Ht is the root of the stationary blade 60, and 100% Ht is the tip of the stationary blade 60.

  Since the operational effects are the same as those of the first embodiment described above, the description thereof is omitted here.

  The stator blades 60 and 70 according to the present invention are preferably used particularly in the subsonic speed stage.

  In the embodiment described above, the code length in the vicinity of 20% Ht and the code length in the vicinity of 80% Ht are shorter than the code length in the vicinity of 50% Ht (in other words, in the vicinity of 20% Ht). However, the present invention is not limited to this. For example, the cord length is around 25% Ht and the vicinity of 75% Ht. The cord length can also be made shorter than the cord length in the vicinity of 50% Ht. Further, the point that the code length of which part is shorter than the code length of which part is a matter that can be changed as necessary.

20 Compression section (Axial flow fluid machine)
60 vane (blade for axial fluid machinery)
61 Leading edge 62 Trailing edge 70 Stator blade (blade for axial fluid machine)
71 Leading edge 72 Trailing edge

Claims (3)

A wing for an axial fluid machine used in an axial fluid machine,
The leading edge protrudes toward the upstream side at the tip portion and the root portion, and the trailing edge is formed to protrude toward the downstream side at the tip portion, the midspan portion, and the root portion, and
When 0% Ht (Ht is the blade height) is the root and 100% Ht is the tip,
The cord length near 20% Ht and the cord length near 80% Ht are formed to be shorter than the cord length near 50% Ht, and
A blade for an axial fluid machine, wherein a cord length in the vicinity of 50% Ht is formed to be substantially equal to a cord length at 0% Ht and a cord length at 100% Ht. A wing for an axial fluid machine used in an axial fluid machine,
The leading edge protrudes toward the upstream side at the tip portion, the midspan portion, and the root portion, and the trailing edge is formed to protrude toward the downstream side at the tip portion and the root portion, and
When 0% Ht (Ht is the blade height) is the root and 100% Ht is the tip,
The cord length near 20% Ht and the cord length near 80% Ht are formed to be shorter than the cord length near 50% Ht, and
A blade for an axial fluid machine, wherein a cord length in the vicinity of 50% Ht is formed to be substantially equal to a cord length at 0% Ht and a cord length at 100% Ht. Axial flow fluid machine characterized in that it comprises an axial-flow fluid machine for blade according to claim 1 or 2.

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